Results
2009-07-12: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 turbofan engines with high-pressure (HP) rotor 4-step air balance piston stationary seals (4-step seals), part numbers (P/Ns) 4923T54G01, 6019T90G03, 6037T99G01, 6037T99G02, and 6037T99G03, installed. This AD requires removing the 4-step seals and incorporating an 8-step seal at the next piece-part exposure. This AD results from the investigation of an airplane accident. Both engines experienced high-altitude flameout. Rotation of the HP rotors was not maintained during descent and the engines could not be restarted. We are issuing this AD to prevent the inability to restart both engines after flameout due to excessive friction of the 4-step seal, which could result in subsequent forced landing of the airplane.
64-19-04: 64-19-04 GENERAL DYNAMICS: Amdt. 783 Part 507 Federal Register August 7, 1964. Applies to Model 240 Series Aircraft. Compliance required within 1,000 hours' time in service after the effective date of this AD, unless already accomplished. A fault in an unprotected cabin supercharger disconnect circuit caused an electrical fire in the cabin pressurization console on the copilot's side. To prevent recurrence of this incident provide the following circuit protection: Modify the aircraft fire extinguisher circuits, cabin pressure dump solenoid circuit and emergency compressor shutoff valve circuit to provide circuit protection and incorporate an alternate emergency power circuit and a normally-off test light in accordance with Convair Service Engineering Report No. 240-24 dated January 3, 1964, with revision "A" dated March 9, 1964, or an FAA Western Region Engineering approved equivalent. (Convair Service Engineering Report No. 240-24 pertains to this same subject.) This directive effective September 7, 1964.
2020-19-05: The FAA is adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Limited (Bell) Model 505 helicopters. This AD requires inspecting each swashplate assembly bearing (bearing), and depending on the inspection results, removing the bearing from service. This AD was prompted by a report of a bearing that migrated out of the swashplate inner ring. The actions of this AD are intended to address an unsafe condition on these products.
79-06-03: 79-06-03 GULFSTREAM AMERICAN (formerly Grumman American Aviation Corporation): Amendment 39-3437. Applies to Model G-159, all serial numbers; and to Model G-1159, serial numbers 1 through 238 and 775, certificated in all categories. Compliance is required prior to further flight, unless already accomplished. To prevent a potential hazard caused by inability to discharge the engine or APU fire extinguisher bottles, accomplish the following: (1) Inspect the cartridge terminals on each aircraft engine and APU fire extinguisher bottle (container) for the presence of electrical shunts. Shunts are installed for safety in shipping and handling and inadvertently may have been left installed. (2) Remove any electrical shunts found on the cartridge terminals, using procedures in the applicable aircraft maintenance manual. Gulfstream American Alert Customer Bulletins No. 11 for Model G-159, and No. 17 for Model G-1159, both dated February 16, 1979, pertain to this subject. This amendment is effective April 2, 1979.
2003-20-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-200 series airplanes, that requires installation of four lanyards on the forward access panel/ door. This action is necessary to prevent the forward ceiling access panel/door from falling down and blocking the aisle, which would impede evacuation in an emergency. This action is intended to address the identified unsafe condition.
78-26-05: 78-26-05 PIPER: Amendment 39-3377. Applies to Piper Model PA-36-285 and PA-36-300, Serial Nos. 36-7360001 thru 36-7760123, 36-7760125 thru 36-7860001, 36-7860003, 36-7860007, 36-7860010 thru 36-7860015 36-7860017 thru 36-7860019, 36-7860021 thru 36- 7860024, 36-7860027 thru 36-7860031, 36-7860034, 36-7860036, 36-7860041, 36-7860043 thru 36-7860045, 36-7860047, 36-7860049 thru 36-7860051, 36-7860061 thru 36-7860063, 36- 7860069, 36-7860071, 36-7860073 thru 36-7860079, 36-7860081 thru 36-7860083, 36-7860086 thru 36-7860114 and 36-7860116 and Model PA-36-375, Serial Nos. 36-7802002 thru 36-7802019, 36-7802021 thru 36-7802023, 36-7802025 thru 36-7802029, 36-7802031, 36-7802040 thru 36-7802042 and 36-7802049 certificated in all categories. To prevent hazards in flight associated with the seizing of rod end bearings in the elevator and aileron control systems, accomplish the following: (a) Within the next ten hours in service from the effective date of this AD or upon the attainment of 50 hours total time in service whichever is later, unless previously accomplished within the previous 50 hours, and at intervals not to exceed 50 hours in service from the last inspection, inspect and replace the rod end bearings in the elevator and aileron system controls in accordance with the "Instructions Section - Paragraphs 1 thru 5" of Piper Service Bulletin No. 608 dated July 11, 1975, or equivalent. (b) Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) Upon the installation of Heim MSS-3D, -4D and -5D rod end bearings for Piper part numbers 452633, 452590 and 452645, respectively, compliance with the inspection requirements of (a) may be canceled. (d) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD.This amendment is effective December 26, 1978.
77-23-09: 77-23-09 PIPER: Amendment 39-3077 as amended by amendment 39-3368. Applies to Models PA-23-250 and PA-E23-250 Serial Numbers 27-2000 to 27-2504 (fuel injected only) and 27-2505 to 27-7754044. Compliance required within 10 hours in service after the effective date of this AD unless already accomplished. In order to prevent fuel flow interruption and engine power loss due to possible adverse fuel vaporization during crossfeed operation, accomplish the following: a. Incorporate the applicable flight manual revision, as listed below, into the FAA-DOA Approved Airplane Flight Manual in accordance with Piper Service Bulletin No. 530: Airplane Flight Manual Revisions No. Model PA-23-250: 27-2000 to 27-2504 Incl. Fuel Injected Only 1204 27-2505 to 27-3943 Incl. 4800# Gross Weight Only 1308 27-2505 to 27-3943 Incl. 5200# Gross Weight Only 1360 27-3837, 27-3944 to 27-4573 Incl. 5200# Gross Weight Only 1520 27-4426, 27-4574 to 27-7554168 Incl. 5200# Gross Weight Only 1630 27-7654001 to 27-7754044 Incl. 5200# Gross Weight Only 1948 Model PA-E23-250: 27-2505 to 27-3943 Incl. 4995# Gross Weight Only 1378 27-3837, 27-3944 to 27-4573 Incl. 4995# Gross Weight Only 1521 27-4574 to 27-7554168 Incl. 4995# Gross Weight Only 1631 b. The Chief, Engineering & Manufacturing Branch, AEA-210, FAA Eastern Region, may adjust the inspection interval specified in this airworthiness directive upon request of an owner or operator submitted with substantiating data through an FAA maintenance inspector. c. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Piper Aircraft Corp., 820 East Bald Eagle Street, Lock Haven, Pennsylvania 17745. These documents may also be examined at FAA Eastern Region Federal Building, JFK International Airport, Jamaica, New York 11430 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and at the Federal Aviation Administration, Eastern Region. (Piper Service Bulletin No. 530, dated December 10, 1976, pertains to this subject.) Amendment 39-3077 was effective November 18, 1977. This amendment 39-3368 is effective December 19, 1978.
2020-19-02: The FAA is superseding Airworthiness Directive (AD) 2000-22-19 for Eurocopter France (now Airbus Helicopters) Model SA330F, G, and J helicopters. AD 2000-22-19 required repetitively inspecting certain tail rotor (T/R) blades for skin debonding and a crack. Since the FAA issued AD 2000-22-19, the inspection procedures have been revised. Additionally, the FAA is adding an affected part-numbered T/R blade and the FAA-validation for Model SA330F and G helicopters has been cancelled. This new AD revises the applicability, requires repetitively inspecting affected T/R blades with the new inspection procedures, and depending on the inspection results, repairing or replacing the T/R blade. This new AD also prohibits installing an affected T/R blade unless it has passed the inspections. The actions of this AD are intended to address an unsafe condition on these products.
79-26-02: 79-26-02 BOEING: Amendment 39-3638. Applies to all Model 737-200 (advanced) airplanes with GPWS flap position switches sensing less than 30 degrees as landing flaps, certificated in all categories. Compliance required as indicated. Accomplish the following: \n\tWithin the next 1,200 hours time-in-service or six (6) months, whichever comes first, after the effective date of this AD, change the ground proximity warning system flap position switch to sense flaps 30 degrees and 40 degrees as the landing flap positions, and provide a flap override switch for landings that must proceed with flap position of 25 degrees or less. This modification may be accomplished in accordance with modifications approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective December 31, 1979.
2003-20-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-400, -500, -600, -700, and -800 series airplanes, that requires either modification of the wiring to the windshield wiper motors in the flight compartment or replacement of those windshield wiper motor/converters with new motor/converters. This action is necessary to prevent a reduction in flight crew visibility due to stalled wiper motors during heavy precipitation and a period of substantial crew workload, which could result in damage to the airplane structure and injury to flight crew, passengers, or ground personnel during final approach for landing. This action is intended to address the identified unsafe condition.